Fluid Mechanics and Flight Mechanics

Enhanced ignition method with synergy of multi-channel gliding arc plasma and fuel injection in a scramjet

  • Jiajian ZHU ,
  • Tiangang LUO ,
  • Yifu TIAN ,
  • Minggang WAN ,
  • Mingbo SUN
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  • Hypersonic Technology Laboratory,National University of Defense Technology,Changsha 410073,China

Received date: 2024-08-05

  Revised date: 2024-09-05

  Accepted date: 2024-10-10

  Online published: 2024-10-15

Supported by

National Natural Science Foundation of China(12322211)

Abstract

Efficient synergy of ignition location and fuel injection is crucial for achieving repeatable enhanced ignition in scramjet combustors. This study proposes an enhanced ignition method involving Multi-Channel Gliding Arc (MCGA) plasma and fuel injection to enhance ignition in a scramjet with an inflow Mach number of 2.92 and a combustor total temperature of 1 590 K. The measurement techniques of multi-view high-speed photography, high-speed schlieren, and electro-optical synchronous high-speed imaging were employed to investigate the effect of ignition position and fuel injection timing on ignition and flame propagation, showing the matching relationship, synergy effect and mechanism between ignition location and fuel injection timing. The experimental results show that the MCGA plasma near the leading edge of the cavity has a good synergy ignition effect with the fuel injection at the establishment stage of the fuel injection. However, when it acts on the rear edge of the cavity, the flame kernel is easy to blow out, the global flame takes a long time to build, and the synergy ignition effect is poor. At the stabilization stage of the fuel injection, the MCGA plasma near the rear edge of the cavity can form an excellent synergy ignition and maintain stable combustion with the fuel injection.

Cite this article

Jiajian ZHU , Tiangang LUO , Yifu TIAN , Minggang WAN , Mingbo SUN . Enhanced ignition method with synergy of multi-channel gliding arc plasma and fuel injection in a scramjet[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2025 , 46(7) : 131037 -131037 . DOI: 10.7527/S1000-6893.2024.31037

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